Tailpiece for aeroplanes



P. I. R. POSTEL-VINAY.

TAILPIECE FOR AEROPLANES. APPLICATION FILED DEC. I9, 1918.

1,373,759. Ptnted Apr. 5, 1921I. I 2 SHEETS-SHEET 2.

Fg 4' I |n l'/ n :"a] \\k /l /l el] F V\ I /J y EN Q W" I I *Yr l. IR l.

N j, .JL (l5/ L A 77/ Ill 1': Ik i: l] :I II Il I.'

.f7/Mil# UN'lf'r-ED sin.'rissA PATENT o'FI-u-:PLv

PIERRE JEAN'RRNE PosTRL-VINAY, or rams, FRANCE, AssIeNoR To s'ooIRrE DRS uorEURs sALMsoN (SYSTEME eAN'roN-UNNE), or BILLANCOURT, FRANCE- TAQLPIECE FOB AEROPLANES.

To aZZwl/m z't'may concern.: Be i 4known that I, PIERRE JEAN BENE PosTEL-VINAY, citizen of the Republic of France .residing at 46 Boulevard de La Tour-Maubourg, Paris, Seine, 1n the Republic of France, have inventedQnew and useful vImprovements in Tallpieces .for Aero lanes, of which the ,following is a spec' cation.v

This invention has for its obyect to provide an improved tail-piece for aeroplanes, which is constituted essentially by a yertical tube serving as a support for the plvotalmembers of the horizontal and vertical rudders, and forming the'end upright of the fuselage to which it is connected by simply engaging the upper and lower longltudlnals into two sockets welded to the said tube by autogenous welding and each formed of a suitably cut and folded metal plate.

The connection to thefuselage is assured by the pull of the stay wires attached to the sockets.

This manner of fixing without bolts avoids the reduction of the section of the longitudinals at their ends, while givlng the desired strength to the assemblage.

lin the accompanying drawings given by wa of example:

Figures .1, 2 and 3 are respectively a side elevation, a plan and a perspective view of a tail-piece in accordance with thls invention.

Figs. 4 and 5 are respectively a sideelevation and a plan showing the mounting of the horizontal and vertical rudders on the tail-piece.

On reference to the drawings it will be perceived that two sockets b and c are welded by autogenous welding on the tube a that constitutes the end upright of the fuselage. rlhese sockets are formed of metal plates suitably Vfolded and cut, into which the upper longitudinals d and lo-wer longitudinals e are engaged, and to which the stay wires f and g are fixed that constitute the connection to the fuselage.

A tube welded by autogenous welding, extends through the tube a at right angles to the axis o-f the latter. This tube 7L carries two bearings z' for the tubular shaft y' of the horizontal rudder is.

' shown in Fig. 3).

` Specification oLetters Patent.

(The shaft j is not l Patented Apr. 5, 1921.

.Application filed DcceM 19, 1918. Serial No. 267,545.

tube a by means of an arrangement of pivots mandmu@ The rigidity of the mounting ofthe rudders 7c and l 1s assured by a triangular bracing comprising a tube n, two tubes o andy stay wires p.

The sockets b and c may comprise recesses g for the purpose of lightening the whole. l Having now described my invention, what I claim as new and desire to secure by Letters Patent is: i 'l l. A tail-piece for. aeroplanes comprising 1n combination an end upright, vmetal ttings iixed'to the ends of said upright, these fittings belng each made in one piece and having each two separate straight recesses Vindependent from. each other, each having the shape of the section of the longitudinals of -the fuselage, said recess being arranged accordlngl to a V in which the ends of the upper and llower longitudinals of the fuselage may be engaged and stay wires connecting the fitting to the fuselage.

2. A tail-piece for aeroplanes comprising 1n combination an end upright, metal ttings fixedl at theends-of said upright, said fittings belng each made in one piece and having each two separate recesses arranged according to a V in which the ends of the upper and lower longitudinals of the fuselage may be engaged, stay wires connecting said fittings to the fusela e, and means upon said upright for supporting the horizontal and vertical rudders so that they may be lcapable of pivoting.

carried by the ends of said support, an axle journaled on said bearings and upon which the horizontal rudder may be fixed, and vertical pivots provided for at the upper and -lower end of the upright and upon which the vertical rudder is adapted to be pivoted. 4. A tail-piece for aeroplanes, comprising in combination an end upright, metal fit1 means connecting 'said fittin lage, a transverse horizontal' support fixed to thei end upright, bearings carriedl by tlfiev ends of said supporta-an axle 'ournaled on saidzbearngs and upon which t e horizontal rudder is adapted to be fixed, vertical pivots provided for at'the upper and lower end of\ upright and upon which the vertical rudder is adapted to be pivoted, lateral struts Connecting the said axle of thel horizontalrudder 'Ito the fuselage, stay wires connecting said axle to said'upper pivot and a strut arranged in the longitudinal pl-an pivot to the `Jfuselage.

.of the apparatus and connecting said upper In testimony -WhereofI' lia'ye vsigned my 20 specification.`

name to this lmamut JEAN RENE PosTEL-vmAY. 

